18 TH INTERNATIONAL CONFERENCE ON COMPOSITE MATERIALS EFFECTS OF PLY CLUSTERING IN LAMINATED COMPOSITE PLATES UNDER LOW-VELOCITY IMPACT LOADING E.V. González 1 *, P. Maimí 1 , P.P. Camanho 2 , A. Turon 1 , J. Costa 3 1 Department of Engineering Mechanics, University of Girona, Girona, Spain, 2 Department of Engineering Mechanics, University of Porto, Porto, Portugal, 3 Department of Physics, University of Girona, Girona, Spain, * Corresponding author ( emilio.gonzalez@udg.edu ) Keywords : ply clustering, polymer-based laminated composite, low-velocity impact, CAI, finite element 1 Introduction Finally, FE simulations of the drop-weight impact This work presents a complete study of the effects of and the CAI tests are performed by using well-suited ply clustering on monolithic, flat and rectangular constitutive models formulated in the framework of polymer-based laminated composite plates with Continuum Damage Mechanics. In detail, an conventional stacking sequences, subjected to a interlaminar constitutive model to describe the drop-weight impact loading. Basically, three main delamination, and an intralaminar constitutive model tasks are addressed in order to analyze the effects of to describe the matrix cracking and the fiber ply clustering on the damage resistance and on the breakage damage mechanisms, are used. The damage tolerance of the structure, which are: (1) purpose of these simulations is double: on the one analytical description of the impact test, (2) design hand, to validate the suitability of the numerical and realization of an experimental test plan, and (3) simulations by comparing with the experimental the performance of finite element (FE) virtual tests. data, and on the other hand, to provide more Due to the simplicity of the structure, the analytical clarifying information to analyze the experimental description of the impact event is feasible. The results. analytical description presented comprises models which predict the elastic response, and models 2 Analytical Prediction And Tests Definitions which predict the threshold load at which significant To determine the maximum elastic impact load, the damage starts. To bridge the analytical elastic impact characterization diagram proposed by Yigit prediction of the impact and the onset of damage, the maximum elastic impact force is typically used, and Christoforou is used [1]. Given an impact configuration, the diagram predicts the behavior type and it is compared with a damage threshold and the maximum impact force by calculating only allowable. Damage occurs if the predicted elastic two key dimensionless parameters: λ (relative impact force is greater than an appropriate threshold stiffness) and ζ w (relative mobility [2]). They are for the corresponding dynamic response type. The analytical description is suitable for preliminary respectively defined as: design analysis, as it enables the fast assessment of k the role that each parameter plays in the impact λ = bs (1) k event. In this sense, the analytical description is used α mainly for the definition of the experimental test plan. k M 1 ζ = α On the other hand, the experimental test plan covers: i (2) w * 16 I D non-destructive inspections (NDI) for the detection 1 of manufacturing flaws, drop-weight impact tests, where k bs is the bending-shearing plate stiffness, k α NDI inspections after impact to assess the damage is the stiffness of the contact law which relates the resistance, and finally, compression after impact impact load with the indentation of the impactor on (CAI) tests to assess the damage tolerance of the the plate, M i is the impactor mass, I 1 is the plate structure. mass divided by the in-plane area. The term D * is
called effective plate stiffness (for more details, see Mechanics (LEFM) and assumes that mode II [1]). fracture determines delamination growth in a simply The diagram is shown in Fig. 1 and represents the supported circular plate. To simplify the variation of the maximum normalized impact force development of the model, static loading conditions were considered, the laminate was treated as F as a function of the relative mobility parameter max isotropic, and only small deflections were ζ w . Four different regions can be identified in the considered. Knowing that G IIc is the fracture diagram those define four different impact toughness in pure mode II, the criterion is defined behaviors. Impact configurations which define as: points in the right part of the diagram behave as quasi-static. For points which fall close to the dashed * 32 D G F = π curve behave as in-plane infinite plate. Between the IIc (3) d 3 quasi-static and the infinite plate behaviors there is a transition zone where the resulting response is a The ASTM D7136/D7136M-05 [4] test method for combination of both behaviors. Finally, the points measuring the damage resistance of a fiber- that fall close to the maximum dimensionless force reinforced polymer matrix composite when result in the half-space behavior, i.e. the plate subjected to a drop-weight impact event is taken as a response is neglected. reference in order to fix some of the governing parameters. The standard is focused on rectangular, flat and monolithic laminated composite plates with 150 mm x 100 mm in-plane dimensions. The specimens are placed over a flat support fixture base with a 125 mm x 75 mm rectangular cut-out which allows the impactor to contact through the specimen without interferences. The support fixture base has four rubber-tipped clamps which restrain the specimen during impact. The boundary conditions provided by the edge supports can be approximated to simply supported. The stacking sequences proposed here to study the ply clustering effect are [(45/0/-45/90) 4 ] S , [(45 2 /0 2 /- 45 2 /90 2 ) 2 ] S , and [45 4 /0 4 /-45 4 /90 4 ] S (in the following, these laminates are respectively identified as L1, L2, Fig.1. Impact characterization diagram (after [1]). and L4). The plate stacking sequence is defined by taking the 0º fiber orientation aligned with the longer In order to demonstrate the validity of the in-plane dimension of the plate. All laminates have characterization diagram, several impact situations the same plate thickness h because an equal number covering all behavior type regions were predicted by of plies is used (i.e. 32 plies; h = 5.8 mm). However, Yigit and Christoforou [1], by numerical integration the ply thicknesses h p are different (i.e. L1: h p = h pp , of a complete analytical model which considers L2: h p = 2 h pp , and L4: h p = 4 h pp , where h pp is the classical laminated plate theory, simply supported thickness of a single pre-preg ply), yielding to boundary conditions and a linear contact law. As different number of interfaces for delamination (i.e. shown in Fig. 1, the simulations follow reasonably L1: n = 30, L2: n = 14, and L4: n = 6). The plates well the trends of the characterization diagram, were manufactured using Hexply AS4/8552 carbon- although in the transition zone, a complete analytical epoxy unidirectional pre-preg. model is required in order to better describe the Three different impact energies E i are considered: response. 19.3 J, 28.6 J, and 38.6 J. Given that the impactor The analytical criterion used for the onset of the mass is kept constant at 5 kg, the different energies delamination was proposed by Davies and Robinson also enable the study of the effects of velocity. Since [3]. The model is based on Linear Elastic Fracture the repeatability of the impact test is quite good, a
Recommend
More recommend
